Supersonic boundary layer transition induced by self-sustaining dual jets

To promote high-speed boundary layer transition,this paper proposes an active self-sustaining dual jets(SDJ)actuator utilizing the energy of supersonic mainflow.Employing the nanoparticle-based planar laser scattering(NPLS),supersonic flat-plate boundary layer transition induced by SDJ is experimentally investigated in an Ma-2.95 low-turbulence wind tunnel.Streamwise and spanwise NPLS images are obtained to analyze fine flow structures of the whole transition process.The results reveal the transition control mechanisms that on the one hand,the jet-induced shear layer produces unstable Kelvin–Helmholtz instabilities in the wake flow,on the other hand,the jets also generates an adverse pressure gradient in the boundary layer and induce unstable streak structures,which gradually break down into turbulence downstream.The paper provides a new method for transition control of high-speed boundary layer,and have prospect both in theory and engineering application.

Dilution characteristics of dual buoyant jets in wavy cross-flow environment

Due to the difference in density between the discharge effluent and coastal water,partially treated wastewater is often discharged into the marine environment as a buoyant jet via submarine outfalls with multiport diffusers.The dilution characteristics of effluent discharge(dual buoyant jets)in a wavy cross-flow environment were studied in a laboratory.The planar laser-induced fluorescence technique was used to obtain the concentration data of the jets.The effects of different environmental variables on the diffusion and dilution characteristics of the jets were examined through physical experiments,dimensional analysis,and empirical formulations.It was found that the dilution process of the dual jets could be divided into two components:the original jet component and the effluent cloud component.The jet-to-current velocity ratio was the main parameter affecting the concentration levels of the effluent cloud.The merging of the two jets increased the jet concentration in the flow field.When the jets traveled further downstream,the axial dilution increased gradually and then increased significantly along the axis.Under the effects of strong waves,the concentration contours branched into two peaks,and the mean dilution became more significant than under the effects of weak waves.Therefore,the dilution of the effluent discharge was expected to be significant under strong wave effects because the hydrodynamic force increased.A dilution equation was derived to improve our understanding of the dilution process of buoyant jets in a wavy cross-flow environment.This equation was used to determine the influences of the jet-to-current velocity ratio,wave-to-current velocity ratio,and Strouhal number on the minimum jet dilution.It revealed that the wave and buoyancy effects in effluent discharges were significant.

Investigation on the Separated Turbulent Flow Field in Dual Rectangular Jets

In the present paper, the flow field of dual rectangular jets was numerically simulated by solving the full Reynolds averaged Navier Stokes equations , where the RNG k ε model and the finite volume method were used. The flow structure in dual rectangular jets and the effects of the velocity were investigated. The numerical results agree qualitatively with the experimental data.

Two-dimensional numerical study of an atmospheric pressure helium plasma jet with dual-power electrode

In this paper, the characteristics of an atmospheric pressure helium plasma jet generated by a dual-power electrode （DPE） configuration are investigated by using a two-dimensional fluid model. The effect of a needle electrode on the discharge is studied by comparing the results of the DPE configuration with those of the single ring electrode configuration. It is found that the existence of the needle leads to the generation of a helium plasma jet with a higher propagation velocity, higher species density, and larger discharge width. Furthermore, the influences of the needle radius and needle-to-ring discharge gap on the generation of a plasma jet are also studied. The simulation results indicate that the needle electrode has an evident influence on the plasma jet characteristics.

Numerical investigation of the interaction of the turbulent dual-jet and acoustic propagation

In order to study the interaction between two independent jets, a three-dimensional（3D） transient mathematical model is developed to investigate the flow field and acoustic properties of the two-stream jets. The results are compared with those of the single-stream jet at Mach number 0.9 and Reynolds number 3600. The large eddy simulation（LES） with dynamic Smagorinsky sub-grid scale（SGS） approach is used to simulate the turbulent jet flow structure. The acoustic field is evaluated by the Ffowcs Williams–Hawkings（FW-H） integral equation. Considering the compressibility of high-speed gas jets, the density-based explicit formulation is adopted to solve the governing equations. Meanwhile, the viscosity is approximated by using the Sutherland kinetic theory. The predicted flow characteristics as well as the acoustic properties show that they are in good agreement with the existing experimental and numerical results under the same flow conditions available in the literature. The results indicate that the merging phenomenon of the dual-jet is triggered by the deflection mechanism of the Coanda effect, which sequentially introduces additional complexity and instability of flow structure. One of the main factors affecting the dual-jet merging is the aperture ratio, which has a direct influence on the potential core and surrounding flow fluctuation. The analysis on the noise pollution reveals that the potential core plays a fundamental role in noise emission while the additional mixing noise makes less contribution than the single jet noise. The overall sound pressure level（OASPL） profiles have a directive property, suggesting an approximate 25° deflection from the streamwise direction, however, shifting toward lateral direction of about 10° to 15° in the dual-jet. The conclusion obtained in this study can provide valuable data to guide the development of manufacturing-green technology in the multi-jet applications.

Deposition of organosilicone thin film from hexamethyldisiloxane(HMDSO)with 50kHz/33MHz dual-frequency atmospheric-pressure plasma jet

The deposition of organosilicone thin films from hexamethyldisiloxane（HMDSO） by using a dual-frequency （50 kHz/33 MHz） atmospheric-pressure micro-plasma jet with an admixture of a small volume of HMDSO and Ar was investigated.The topography was measured by using scanning electron microscopy.The chemical bond and composition of these films were analyzed by Fourier transform infrared spectroscopy （FTIR） and x-ray photoelectron spectroscopy.The results indicated that the as-deposited film was constituted by silicon,carbon,and oxygen elements,and FTIR suggested the films are organosilicon with the organic component （-CHx） and hydroxyl functional group（-OH） connected to the Si-O-Si backbone.Thin-film hardness was recorded by an MH-5-VM Digital Micro-Hardness Tester.Radio frequency power had a strong impact on film hardness and the hardness increased with increasing power.

Numerical Investigation on a Dual-jet Consisting of a Plane Wall Jet and a Parallel Offset Jet at Low-Reynolds Number

A dual-jet consisting of a wall jet and an offset jet has been numerically simulated using lattice Boltzmann method to examine the effects of jet spacing between two jet centerlines,defined as s.The Reynolds number based on jet-exit-width dis set to be Re = 56 and the jet spacing is set to be less than or equal 10 times the jet-exitwidth.Computational results reveal that the flow field displays periodic vortex shedding when the jet spacing is in the range of 9≤s/d ≤ 10,while it remains steady with two counter-rotating vortices in the converging region when s/d ≤ 8.When s/d = 9,the power spectral analyses indicate that the vortex shedding phenomenon has specific frequency.The significant oscillation stresses induced by the periodic components of velocities are found to mainly exist in the inner shear layer regions,implying stronger momentum transfer occuring in these regions.

多源观测资料在六盘山西侧一次强对流暴雨中的应用

利用常规气象探测、ERA5逐1 h再分析、区域气象站、X波段双偏振、C波段多普勒及风廓线雷达等多源资料,对2022年7月15日六盘山西侧发生的一次被业务常用数值模式和预报员主观预报均漏报了的强对流暴雨进行综合分析。结果表明:此次暴雨发生在西太平洋副热带高压西北侧,主要落区为低层暖式切变线南侧及低空急流左前侧。在六盘山地形作用下,中尺度地面辐合线、中尺度西南急流和中尺度涡旋可能是此次暴雨的重要触发、维持和增强系统。暴雨由两条中尺度回波带造成,其上对流单体呈后向传播,存在明显的列车效应。地面5 min降水量明显增强前1~2 h,有低空急流加强、垂直风切变增加、急流中风速向下脉动和干侵入等现象,对暴雨预报预警有很好的参考意义。50 dBz以上强度回波面积、垂直积分液态水含量、回波顶高、大范围的差分传播相移(K_(DP))和差分反射率因子(Z_(DR))的大值区对强降水落区有较好的指示意义,K_(DP)能较好反映强降水强度。最大K_(DP)和Z_(DR)均较最强5 min降水提前10 min出现,Z_(DR)弧和Z_(DR)柱也较最强5 min降水提前10~20 min出现。最强降水时段,K_(DP)达3.0~4.0°·km^(-1),对应Z_(DR)为3.0~3.3 dB,相关系数为0.90~0.95,说明雨滴直径大且数浓度大,增加了降水的极端性。

双模毁伤元JET&JPC转换成型机理研究

针对双模毁伤元JET和JPC转换成型问题,理论计算点、环两种不同起爆方式下爆轰波的作用过程,采用LS-DYNA仿真软件计算分析了起爆方式、装药结构、药型罩结构对双模毁伤元JPC和JET成型的影响,并正交设计双模毁伤元JET和JPC。研究表明:双模毁伤元JPC和JET成型差异显著,70μs时刻JPC毁伤元头部速度5268m/s,长径比9.06;JET毁伤元头部速度8353m/s,长径比25.73;双模毁伤元速度差达到3085m/s,长径比比值达到2.84倍。

应用Dual PDA研究同轴交叉射流轴线速度衰减

采用Ｄｕａｌ ＰＤＡ研究了２种射流交叉角度和４种密度比的同轴交叉射流的流场，发现射流交叉角度和密度比对射流流场有重要影响。提出了考虑了径向流动速度、密度差别的基于动量守恒的当量直径和当量速度。当量速度与实验结果较为吻合．对充分发展的射流，该法可较好的描述射流交叉角度、密度比对轴线上轴向速度的影响。

Computational Film Cooling Effectiveness of Dual Trench Configuration on Flat Plate at Moderate Blowing Ratios

在现在的工作，计算模拟用 ANSYS CFX 被做在与双沟使性能凉下来的电影预言改进。双沟的配置一起由二条沟组成，一条更宽的沟和其它是从更宽的渗出的狭窄的沟。在范围(0.5:5 ) 的几刮比率被调查。2.775 的 pitch-to-diameter 比率被使用。由使用双沟配置，冷却剂喷气影响了允许增加在沟旁边地传播冷却剂的沟墙 two times，减少完全在表面上盖住的喷气速度和喷气。当刮的比率增加了，结果显示这种配置增加了断热的有效性。空间地平均的断热的有效性到达了 57.6% 为在 M= 2。没有观察电影容易的根本刮的比率。双沟大小写的断热的电影有效性超过了狭窄的沟案例， laidback 在不同刮的比率的扇形的洞，扇形的洞和柱体洞。

双直喷型柴油JCCI模式的参数优化数值模拟

针对双直喷型柴油射流控制压燃模式,利用三维数值模拟结合优化算法,分析了预喷正时、射流正时、初始温度、初始压力和预喷射能量比等参数对发动机燃烧与排放性能的影响.计算结果表明,射流正时可以有效控制着火相位和燃烧相位,预喷正时主要影响预混合气燃烧后期.当燃烧相位在6~8°CA ATDC区间时,发动机经济性最佳.射流正时和预喷正时均较晚时,燃烧呈现两阶段高温放热过程,整体燃烧速率大于射流正时与预喷正时均较早的单阶段高温放热过程,因此等效燃油消耗率下降6.80 g/(kW·h).

双平行平面射流与环境流基元反应特性研究

为揭示双射流与环境流之间流动-化学反应耦合过程的标量输运机理,采用大涡模拟方法对具有二级非平衡基元反应(A+B→R)的双射流与环境流反应工况进行了研究,达姆科勒数Da为1且雷诺数为2000。首先通过对反应性单射流进行数值模拟,将平均流向速度和平均混合浓度分数等统计量与现有方法结果进行对比,验证了数值方法的准确性;其次,基于化学反应标量输运方程研究了反应性双射流流动-化学反应耦合过程中的标量输运和化学反应特性。结果表明:流场上游湍流/非湍流界面(T/NTI)附近存在1个急剧消耗环境流中反应物B的区域,T/NTI的卷吸过程深刻影响着化学反应;化学反应主要发生在流场上游,T/NTI附近某一时刻产物R的非稳态变化几乎由化学反应产生和对流输运过程决定,而流场下游湍流区域某一时刻产物R的非稳态变化主要取决于对流作用;统计平均下,在6<x/d<20范围内,流场流向对流作用和法向对流作用对产物R的输运收支平衡。

Optical Spectroscopic Investigation of Ar/CH_3OH and Ar/N_2/CH_3OH Atmospheric Pressure Plasma Jets

Ar/CH3OH and Ar/N2/CH3OH plasma jets were generated at atmospheric pressure by dual-frequency excitations. Two different cases were studied with focus laid on the generation of CN radicals. In one case Ar gas passed through a bubbler with saturated methanol steam but without addition of N2 （Ar/CH3OH plasma）. In the other case N2 passed through the bubbler with saturated methanol steam （Ar/N2/CH3OH plasma）. The optical emission lines of CN radicals have been observed in these two cases of plasma discharges. The addition of N2 can significantly increase the optical emission intensity of CN bands.

基于合成双射流的襟翼舵效增强技术研究

飞机在起降和大机动过程中,襟翼偏角过大会导致襟翼上方出现流动分离,从而使舵面效率降低甚至失效。为有效解决舵效问题,提出了一种基于合成双射流的襟翼舵效增强技术,针对无缝襟翼,探究了合成双射流不同控制参数对升力、舵效的影响规律。研究结果表明:合成双射流能在襟翼表面形成周期性涡结构,增强边界层底部低速流体与主流的动量交换,提高边界层抗逆压梯度的能力;襟翼处合成双射流可有效提高升力、增强舵效;当合成双射流无量纲驱动频率为3.89、动量系数为3.01×10–3时,舵效增强效果最好。此外,还设计、制作了合成双射流激励器与机翼一体化模型,并开展了飞行试验,可实现的滚转角速度达15.69(°)/s,验证了合成双射流增强舵效的可行性和有效性。

尾部喷流对飞行器阻力影响的数值模拟分析

底阻在弹类飞行器阻力中占比较大,准确预示底阻对于弹类飞行器飞行性能评估至关重要,而发动机尾部喷流对底阻影响明显。采用基于雷诺平均Navier-Stokes方程的流场仿真方法研究了飞行器底部发动机喷流和外流干扰流场特性,主要分析了喷流对飞行器阻力的影响。飞行器安装了两台推力可调的液体火箭发动机,发动机在不同飞行工况下采用不同推力工作。分别研究了亚音速、跨音速和超音速典型飞行工况下弹体底部无喷流状态、单喷管喷流状态和双喷管喷流状态时,飞行器阻力变化情况。结果表明:不同马赫数下,发动机喷流对底部阻力影响情况基本一致,与无喷流情况相比,当发动机工作时,无论单喷管喷流还是双喷管喷流状态,底部发动机喷流引射效应明显,弹体阻力系数明显增加。

双喷气自循环机匣处理对对转压气机性能的影响

为发展适用于对转压气机变转速比工况下的扩稳技术,基于某两级对转压气机设计出一种新型双喷气自循环机匣处理结构,能够实现在不同转速比下提高对转压气机的失速裕度。在设计转速比下研究了轴向喷气位置对自循环机匣处理扩稳能力的影响,并选取扩稳性能最佳的双喷气自循环机匣处理方案探究其在变转速比工况下的扩稳潜力。研究结果表明,在设计转速下,双喷气自循环机匣处理主要改善后排转子的叶顶流场,失速裕度最大提高8.40%;在非设计转速比下,双喷气自循环机匣处理可将失速裕度提升8.71%~9.74%。双喷气自循环机匣处理的双射流将叶顶泄漏流和主流的交界面推向下游,同时改善了两转子的叶顶流场品质,从而推迟失速的发生。

合成双射流冲击平板流场结构与模态分解分析

为揭示合成双射流冲击平板流场结构特征,通过大涡模拟方法对合成双射流冲击平板流动进行了仿真,采用有限时间Lyapunov指数方法对流场的拉格朗日涡结构进行了识别,并与欧拉框架下的速度矢量和涡量结果进行了对比分析。结果表明,在合成双射流两股射流交替作用下,射流核心区涡系结构较为复杂且涡量丰富,远离核心区存在一对稳定的涡结构,且拉格朗日涡结构与涡量对应较好,为合成双射流冲击冷却的布局设计提供了指导。另外,流场本征正交分解表明,第一阶模态关于激励器出口中心轴线大致对称,其能量占总体能量的35%,前6阶模态的能量占80%;根据前6阶模态所反映的流场特性,合成双射流冲击平板流场具有高度的对称性。

S弯进气道合成双射流流场控制特性分析

针对飞翼布局无人飞行器中S弯进气道明显流动分离和出口总压畸变等问题,提出了基于合成双射流的主动流动控制方法,建立了合成双射流的S弯进气道数值仿真模型。结果表明,在S弯进气道分离点附近施加合成双射流控制,在整个射流周期内通过“吹”“吸”接力可以有效抑制边界层流动分离,有效提升总压恢复系数。对比研究了合成双射流不同射流角度、射流峰值速度和激励频率对S弯进气道流场控制特性的影响规律。结果表明合成双射流与主流的角度越小,流动分离控制效果越好,较大射流峰值速度会对主流形成“阻挡”致使控制效果下降,激励频率与流场特征频率越接近控制效果越明显。